Elastic correction method of airplane lifting resistance aerodynamic characteristics

Abstract

The invention discloses an elastic correction method of an airplane lifting resistance aerodynamic characteristics, which is characterized by comprising the following steps of: step 1, obtaining lifting force of a rigid wing; step 2, obtaining a lifting force correction formula; step 3, obtaining the resistance of the rigid wing; step 4, obtaining a resistance correction formula; and step 5, obtaining a correction parameter according to wings of different airplanes, and correcting the lifting force and the resistance of an airplane. According to the elastic correction method, the provided correction formulas are simple and clear to express by taking that the lifting force correction formula and the resistance correction formula of the airplane are finally provided as an aim, so that the elastic correction method is suitable for the airplane with a large span-chord ratio wing to carry out numerical value pneumatic calculation on a rigid model and elastic correction on lifting force and resistance properties characteristics after a wind tunnel test, and has higher correction precision on the airplane with the large span-chord ratio wing.

Description

technical field [0001] The invention relates to an elastic correction method for lift-drag aerodynamic characteristics of an aircraft, which belongs to the technical field of aviation aircraft. Background technique [0002] When the aircraft is subjected to aerodynamic loads during flight, the body structure, especially the wings, will undergo elastic deformation, which belongs to the static aeroelasticity problem of the aircraft. For aircraft with small aspect ratio wings, elastic deformation has little influence on the aerodynamic characteristics of the whole aircraft, which can be ignored, but for aircraft with large aspect ratio wings (aspect ratio > 15), relatively large Large elastic deformation, the entire wing will produce a large upturn and torsional deformation, this static aeroelastic deformation cannot be ignored. At present, all aerodynamic characteristic calculations and wind tunnel tests are performed on the aircraft as a rigid body. The aerodynamic data o...

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Problems solved by technology

For aircraft with small aspect ratio wings, elastic deformation has little influence on the aerodynamic characteristics of the whole aircraft, which can be ignored, but for aircraft with large aspect ratio wings (aspect ratio > 15), relatively large Large elastic deformation, the entire wing will produce a large upturn and torsional deformation, this static aeroelastic deformation cannot be ignored

At present, all aerodynamic characteristic calculations and wind tunnel tests are performed on the aircraft as a rigid body. The aerodynamic data obtained are the results of the rigid model. This result deviates from the aerodynamic performance of the real aircraft. It is necessary to find a The elastic aerodynamic correction method is used to correct the lift and drag characteristics of the aircraft obtained from the rigid model and wind tunnel test

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